Baseline architecture:
Baseline architecture Spacecraft diameter 2.67 m
Mass Spacecraft Bus: 310 kg
Mass Payload: 232 kg
Power: 800 W
Data: 30 kbs
Spacecraft layout:
Spacecraft layout
Thruster requirements:
Thruster requirements Surface: 5.6 m2, effective surface 4.8 m2
Solar radiation: 1.376 kW/m2
DC force: 20 μN, to be compensated by thrusters (50 μN req.)
Noise sets requirements on DFACS and thruster noise
Thruster noise requirement:
Thruster noise requirement
DFACS performance:
DFACS performance Example: relative acceleration between the two testmasses
DFACS performance:
DFACS performance All requirements are met in the current design
Noise sources are taken from LPF
Cross talk
Magnetics
Charging
Surface effects
No ‘miracles’ needed
Inertial sensor design:
Inertial sensor design Design is a copy of the present LPF design
No significant design changes foreseen
LISA modelling relies on LISA PF performance:
Shielding
Material properties (bulk and surface)
Mass and power
Footprint
Notable exception: Charging, gravitational balancing, details of the actuation law.
Room for additional hardware:
Room for additional hardware Requirements:
No additional mass
No additional power
No additional data rate
All present budgets hold margins suitable for the programmatic stage of the project (mass, power ~ 30%)
Definition of the system architecture is not finalised
Additional hardware can be accommodate if mission or mission science profit from it.